Research of numerical simulation method in temperature and thermal stress of short range high speed missile

Using engineering estimating method, one stead aerodynamic heating of high speed missile was calculated. Adopting aerodynamic and interior heat transfer of wall missile, heat flux equation was made, and then the temperature-time distribution of along missile was obtained. Based on the special flight condition, the distribution transient temperature field was obtained, as the temperature boundary condition of transient thermal analysis. At the temperature gradient along thickness or not, thermal stress was calculated. Result shows that this method is fast and effective, and applies in concept research and multiple objective design of high speed of short range missile.